US3262269A - Thrust reverser - Google Patents

Thrust reverser Download PDF

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Publication number
US3262269A
US3262269A US462791A US46279165A US3262269A US 3262269 A US3262269 A US 3262269A US 462791 A US462791 A US 462791A US 46279165 A US46279165 A US 46279165A US 3262269 A US3262269 A US 3262269A
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US
United States
Prior art keywords
wall
aft
duct
fan
cascades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US462791A
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English (en)
Inventor
John T Kutney
Jr George H Israel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US462791A priority Critical patent/US3262269A/en
Priority to GB15270/66A priority patent/GB1147351A/en
Priority to FR61011A priority patent/FR1479132A/fr
Priority to BE682005D priority patent/BE682005A/xx
Priority to CH807266A priority patent/CH446078A/de
Priority to NL6607772A priority patent/NL6607772A/xx
Priority to DEG47104A priority patent/DE1287444B/de
Application granted granted Critical
Publication of US3262269A publication Critical patent/US3262269A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B64C25/423—Braking devices acting by reaction of gaseous medium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/68—Reversers mounted on the engine housing downstream of the fan exhaust section
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the high bypass ratio turbofan of about 4 to l and above, is a fan engine in which a vary large quantity of the propulsive fluid is sent through the annular bypass duct.
  • thrust reversers must perform two functions. They must stop the low and they must turn the ow into the reverse position. It is desired to do this where there is as little disturbance or change as possible in the normal aerodynamic members that are required for other engine functions.
  • the aircraft geometry has been compromised to reect the physical mass of the reverser unit.
  • it-is desired ⁇ to provide a reverser that will t the aircraft structure as it exists for other aerodynamic functions.
  • a thrust reverser supply good thrust modulation characteristics to provide for immediate and full thrust in the case of a wave-off or go-around condition during a landing operation.
  • the engine be kept operating at its full thrust output and that the thrust reverser be such that it provides reverse thrust and can be immediately inactivated without he need for changing engine speed to resume acceleration.
  • the thrust reverser should be fail-safe so that it will assume an inoperative and cruise position in the event of structural failure.
  • the main object ofr the present invention is to provide a thrust reverser that is applicable to high bypass ratio turbofan-engines and which splits the functions of the thrust reverser both functionally and structurally.
  • Another object is to provide such a reverser which maintains constant flow exhaust area from the bypass duct from forward cruise to full reverse and all modulated reverse in between.
  • a further object is to provide such a reverser which employs substantially the existing fan structure without compromising any of the aerodynamic characteristics desired for other functions.
  • a further object is to provide such a reverser in which a lightweight linkage mechanism, that is housed out of the ow and within a supporting strut, cntrollably inter- 3,262,269 Patented July 26, 1966 connects the two functional structures so as to maintain the constant area and all of which is easily movable by a simple actuator.
  • the invention is directed to use in a jet propulsion powerplant of the fan type having an inner wall and a fan concentric with the wall and extending radially beyond the wall.
  • This may be an aft or a forward fan engine when the wall encloses an engine.
  • a thrust reverser mechanism is provided which comprises a cowling surrounding the fan and spaced from the wall to form a bypass duct. The cowling is split into forward and aft abutting portions forming inner and outer ow surfaces when in cruise position.
  • a fixed ring of flow reversing cascades is connected to the forward portion at the downstream end thereof and the aft portion telescopes over the fixed cascades so that they are inoperative during cruise. This is the reversing structure.
  • the blocking structure comprises a plurality of peripherally disposed blocker flaps which are pivoted at their upstream ends to the wall for fail-safe operation.
  • a separate actuating means controllably interconnects the aps and the aft cowl portion to rotate the flaps into the duct and simultaneously translate the aft portion downstream to uncover the cascades, the actuating mechanism being so proportioned that it maintains constant flow exhaust area from the duct and reverses the duct ow. Additionally, a simple linkage structure and sealing mechanism is disclosed.
  • FIG. 1 is a view partially in cross-section of a typical front fan powerplant supported from an aircraft wing and employing the instant invention
  • FIG. 2 is an enlarged cross-sectional view in the area of the reverser showing the reversing mechanism in cruise position;
  • FIG. 3 is a view similar to FIG. 2 showing the mechanism moved into reverse thrust position
  • FIG. 4 is a partial perspective view illustrating a sealing mechanism between individual blocker aps.
  • front fan high bypass ratio powerplant is described for illustration and the invention is equally applicable to aft fan powerplants as well as cruise fans. Also, the invention is described in connection with a front fan powerplant with a concentric jet engine wherein the fan nacelle does not extend completely back to the rear of the jet engine wall although the invention is equally applicable to such an installation.
  • High bypass ratio fans are those in which the ratio of the fluid passing through the fan to the jet engine is about 8 to 1 or above. In such installations it may be necessary to reverse only the fan flow for satisfactory performance and the jet engine exhaust may be ignored.
  • FIG. l there is shown a front fan powerplant of the general type that might employ the instant invention.
  • an aircraft structure such as wing 9 may support an engine generally indicated at 10 by means of conventional strut structure 11.
  • Engine 10 may 'be of the front fan concentric type as shown in FIG. l and which employs an inner jet engine 12 discharging through a nozzle 13 to provide thrust.
  • the jet engine is enclosed within a wall 14 in the conventional manner. While described in connection with a concentric fan jet engine it should be noted that wall 14 may be the Iwall of a plug in a pure cruise fan fed from a remote gas generator in a well known manner. For convenience of description, the concentric arrangement will be described.
  • a fari 15 concentric with the engine andextending radially beyond the wall 14 is provided.
  • the fan 15 is surrounded by Cowling 16 which is larger in diameter than the engine and spaced from the engine wall 14 to form a bypass duct 17 for additional thrust by movement of relatively large masses of lower velocity air in the well known manner.
  • this mass of air may be eight or greater times the amount of air flow through the engine 12.
  • the fan air is used to propel fluid through the duct 17 as well as to supercharge the engine 12.
  • the present invention splits the reverser functionally and structurally.
  • the two functions that a reverser must perform are (l) stopping the fiow and (2) turning the ow.
  • the present invention provides structure to perform both of these functions and splits the structure so that two separate but interconnected systems perform the two functions and still maintain the aerodynamic features of the engine substantially undisturbed.
  • Cowling 16 is split peripherally around itself into a forward portion 18 and an aft portion 19. These portions may be generally seen in FIG. 1. Again, in FIG. 2, in the cruise position, the forward and aft portions 18 and 19 are substantially cylindrical and abut generally along line 2t). It will be seen that both portions form the inner and outer flow surfaces in the cruise position of FIG. 2.
  • the engine wall 14 is provided generally with a plurality of peripherally disposed blocker flaps 22 which are pivoted at their forward ends at 23 to wall 14. It is to be noted that the engine wall 14 and aft cowl portion 19 form a nozzle with throat 21 therebetween.
  • a suitable depression is provided in the wall so that the fiaps 22 are retractably nested to form a smooth wall surface in the cruise position as shown in FIG. 2. It will be apparent that these flaps 22 may be quite thin and thus easily actuated and form the smooth flow surface necessary in the FIG. 2 cruise position. Rotation of aps 22 into duct 17 blocks the flow.
  • the second function of reversing the flow is obtained by means of a ring of fiow reversing cascades 24 that are xed to and extend aft from forward portion 18 as shown. It can 'be seen that these cascades, since they are fixed and do not move may be relatively thin and simple in ⁇ construction and easily fit into a thin Cowling structure 16.
  • the reversing function is then performed by these cascades 24 which, in an installation as shown in FIG. 1, may preferably extend completely around the periphery although not limited to a Complete peripheral arrangement. Since reversal is desired it is necessary that aft cowl portion 19 be designed to telescope over cascades 24 so that the cascades are nested or Completely surrounded by the aft cowl 19.
  • the cowl 19 must also be translated downstream to uncover the cascades.
  • a minimum number of peripherally spaced track supports 25 are fixed to the forward portion 18 and extend aft from that portion.'
  • the aft cowl portion 19 may be carried on the track support means in any suitable manner so that the cowl 19 can telescope over and cover the cascades when it is in the abutting forward position as shown in FIG. 1.
  • FIG. 3 the structure is shown in the reversing position. In this position it can be seen that blocker aps 22 .are extended out into ythe bypass duct 17 -to block the fiow and aft portion 19 has been translated downstream to uncover cascades 24 so that the flow is then reversed as shown by the arrows.
  • FIGS. 2 and 3 A typical lightweight and simplified actuating means that will perform this function is disclosed in FIGS. 2 and 3.
  • This actuating means includes a translatable ring 26 that is disposed within the engine wall 14 and out of the iiow. Ring 26 may be guided if necessary by any suitable means such as a track.
  • Blocker liaps 22 are actuated by a first link 27 which connects the translatable ring Z6 and the blocker fiap 22 downstream of the blocker pivot 23 so the blocker fiaps are fail-safe, i.e., will close on structural failure.
  • the means interconnecting the blocker and aft cowl portion 19 includes a bellcrank 2S that is pivoted at 29 within the wall 14 and that extends for the most part within strut 11 which would be In order to move the interconnecting bellcrank 28, there is provided a second link 30 connected to the ring 26 and the link extends forward and is connected to the bellcrank 28 as shown.
  • the aft cowl 19 is ⁇ moved by a link connection 31 which is connected ⁇ with bellcrank ⁇ 2S in any suitable manner as shown.
  • members 28, 30 and 31 may be substantially carried within the strut 11 and bellcrank 28 may be conveniently in the form of an I-I-shaped member for strength with links 3i) and 31 connected therebetween to form a box-like structure which is strong enough to move the entire aft cowl 19 by this single structure and a single actuator.
  • the actuating means is moved by an actuator 32 which is connected to the translatable ring 26 to move the ring downstream from the position shown in FIG. 2 to rotate the flaps 22 into the duct by means of link 27 as shown in FIG. 3.
  • bellcrank 28 is pivoted downstream by link 30 and moves the aft cowl portion 19 through link connection 31 so that as the flaps 22 are rotated the cascades 24 are simultaneously uncovered.
  • link 30 may Ihe proportioned to maintain the constant area for the exhaust of theow from the bypass duct in moving from the ⁇ cruise position of FIG. 2 to the full reverse thrust position of FIG. 3
  • the thrust reverser herein disclosed provides for maintaining the Cowling 16 thin and still permits the reversing function Ito be performed within the cowling which structure must be present for normal engine operation.
  • cascades 24 may be small and may be fixed. They are of simple lightweight and thin construction and perform only a reversing function.
  • the blocking ffunction performed by thin blockers 22 may be separated from the reversing function and conveniently and aerodynamically placed in the engine wall 14 as disclosed with suitable interconnecting and controlled actuating means between the two functions and structures so that constant area is always maintained.
  • thrust reverser mechanism comprising,
  • cowling being split into forward and aft abutting portions forming inner and outer flow surfaces in cruise posi-tion
  • actuating means controllably interconnecting said flaps and aft cowl portion for rotating and extending said flaps into said duct and translating said aft portion downstream for uncovering said cascades and maintaining constant flow exhaust area from said
  • thrust reverser mechanism comprising,
  • cowling being split into forward and aft abutting cylindrical portions forming inner and outer fiow surfaces in cruise position
  • peripherally spaced track support means fixed to said forward portion and extending aft
  • actuating means controllably interconnecting said fiaps and aft cowl portion for rotating and extending said fiaps into said duct and simultaneously translating said aft portion downstream for uncovering said cascades and maintaining constant flow exhaust area from said duct and reversing the duct fiow.
  • Apparatus yas described in claim 6 wherein said aft cowl portion and wall form a nozzle in the abutting position.
  • said actuating means includes a translatable ring within said engine wall, a first link connecting said translatable ring and blocker fiap downstream of said blocker pivot, bellcrank means pivoted within said wall and extending into said strut, a second link connected to said translatable ring and extending forward and connected to said bellcrank, said bellcrank being link-connected with said aft cowl portion, and an .actuator connected to said translatable ring to move said ring downstream and thus rotate said flaps into the duct by said first link, pivot said bellcrank downstream by said second link and translate said aft cowl portion by said bellcrank link connection, said parts being proportioned to rotate said flaps and uncover said cascades and simultaneously maintain a constant area for exhaust of flow from the by-pass duct in moving from cruise to full reverse thrust position.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US462791A 1965-06-07 1965-06-07 Thrust reverser Expired - Lifetime US3262269A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US462791A US3262269A (en) 1965-06-07 1965-06-07 Thrust reverser
GB15270/66A GB1147351A (en) 1965-06-07 1966-04-06 Improvements in thrust reverser for jet propulsion engine
FR61011A FR1479132A (fr) 1965-06-07 1966-05-10 Inverseur de poussée pour moteur de propulsion à réaction
BE682005D BE682005A (enrdf_load_stackoverflow) 1965-06-07 1966-06-02
CH807266A CH446078A (de) 1965-06-07 1966-06-03 Schubumkehreinrichtung
NL6607772A NL6607772A (enrdf_load_stackoverflow) 1965-06-07 1966-06-03
DEG47104A DE1287444B (de) 1965-06-07 1966-06-07 Schubumkehrvorrichtung fuer ein Mantelstromstrahltriebwerk

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US462791A US3262269A (en) 1965-06-07 1965-06-07 Thrust reverser

Publications (1)

Publication Number Publication Date
US3262269A true US3262269A (en) 1966-07-26

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US462791A Expired - Lifetime US3262269A (en) 1965-06-07 1965-06-07 Thrust reverser

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US (1) US3262269A (enrdf_load_stackoverflow)
BE (1) BE682005A (enrdf_load_stackoverflow)
CH (1) CH446078A (enrdf_load_stackoverflow)
DE (1) DE1287444B (enrdf_load_stackoverflow)
GB (1) GB1147351A (enrdf_load_stackoverflow)
NL (1) NL6607772A (enrdf_load_stackoverflow)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3483702A (en) * 1966-06-29 1969-12-16 Rolls Royce Fan thrust reverser for a jet propulsion plant
US3717304A (en) * 1970-05-06 1973-02-20 Rolls Royce Thrust reverser for fluid flow engine
FR2163688A1 (enrdf_load_stackoverflow) * 1971-12-15 1973-07-27 Rolls Royce
US3814324A (en) * 1972-06-19 1974-06-04 Gen Electric Propulsion nozzle and actuator system employed therein
US5615834A (en) * 1995-01-31 1997-04-01 Osman; Medhat A. Ultra thrust reverser system
US20040231317A1 (en) * 2001-09-27 2004-11-25 Dehu Michel Philippe Locking system on a grid thrust reverser
US20090107108A1 (en) * 2006-05-10 2009-04-30 Guy Bernard Vauchel Nacell for bypass engine with high bypass ratio
FR2939477A1 (fr) * 2008-12-10 2010-06-11 Aircelle Sa Nacelle de turboreacteur a section de tuyere variable
US20100269485A1 (en) * 2006-10-12 2010-10-28 Jain Ashok K Integrated variable area nozzle and thrust reversing mechanism
RU2499904C2 (ru) * 2008-04-14 2013-11-27 Эрсель Гондола двухконтурного турбореактивного двигателя
EP2243945A3 (en) * 2009-04-24 2014-03-26 United Technologies Corporation Thrust reverser assembly with shaped drag links
RU2538348C2 (ru) * 2009-11-05 2015-01-10 Эрсель Устройство реверса тяги
US20150107224A1 (en) * 2013-10-17 2015-04-23 Rohr, Inc. Core cowl thrust reverser system and apparatus
US20170198659A1 (en) * 2016-01-13 2017-07-13 Rohr, Inc. Translating cascade hidden blocker door thrust reverser

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1964976C3 (de) * 1969-12-24 1973-01-04 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Schubumkehrvorrichtung für ein Turbinenstrahltriebwerk eines Flugzeuges
US3981450A (en) * 1975-09-22 1976-09-21 The United States Of America As Represented By The Secretary Of The Air Force In-flight modulating thrust reverser
FR3031725B1 (fr) 2015-01-21 2018-06-01 Safran Nacelles Nacelle de turboreacteur d’aeronef
US20160305370A1 (en) * 2015-04-16 2016-10-20 Honeywell International Inc. Translating cowl thrust reverser with door pivots aft of reverse flow path
US10563614B2 (en) 2016-08-17 2020-02-18 Honeywell International Inc. Composite translating cowl assembly for a thrust reverser system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847823A (en) * 1955-03-15 1958-08-19 Curtiss Wright Corp Reverse thrust nozzle construction
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
US2950595A (en) * 1954-11-01 1960-08-30 Marquardt Corp Thrust reverser
US3034296A (en) * 1958-04-02 1962-05-15 Rolls Royce Control mechanism for aircraft jet-propulsion engines having means for producing forward and reverse propulsive thrusts
US3036431A (en) * 1959-09-08 1962-05-29 Boeing Co Thrust reverser for jet engines
US3068646A (en) * 1959-01-28 1962-12-18 Rolls Royce Improvements in by-pass type gas turbine engines
US3113428A (en) * 1957-03-13 1963-12-10 Rolls Royce Silenced jet propulsion nozzle with thrust reversing means

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE524592A (enrdf_load_stackoverflow) * 1952-11-25
DE1054848B (de) * 1956-04-27 1959-04-09 Armstrong Siddeley Motors Ltd Vorrichtung zur Schubumkehr bei einem Strahltriebwerk eines Flugzeugs
FR1286886A (fr) * 1961-01-27 1962-03-09 Nord Aviation Dispositif d'inversion de poussée pour propulseurs comportant un turbo-réacteur àdouble flux
DE1127725B (de) * 1960-01-12 1962-04-12 Rolls Royce Strahltriebwerk mit Mitteln zur Strahlumkehr
DE1187491B (de) * 1960-03-07 1965-02-18 Moteuers D Aviat Soc Nat D Etu Stroemungskanal mit ringfoermigem Querschnitt und seitlichen Strahlumlenkungsoeffnungen

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2950595A (en) * 1954-11-01 1960-08-30 Marquardt Corp Thrust reverser
US2847823A (en) * 1955-03-15 1958-08-19 Curtiss Wright Corp Reverse thrust nozzle construction
US3113428A (en) * 1957-03-13 1963-12-10 Rolls Royce Silenced jet propulsion nozzle with thrust reversing means
US3034296A (en) * 1958-04-02 1962-05-15 Rolls Royce Control mechanism for aircraft jet-propulsion engines having means for producing forward and reverse propulsive thrusts
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
US3068646A (en) * 1959-01-28 1962-12-18 Rolls Royce Improvements in by-pass type gas turbine engines
US3036431A (en) * 1959-09-08 1962-05-29 Boeing Co Thrust reverser for jet engines

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3483702A (en) * 1966-06-29 1969-12-16 Rolls Royce Fan thrust reverser for a jet propulsion plant
US3717304A (en) * 1970-05-06 1973-02-20 Rolls Royce Thrust reverser for fluid flow engine
FR2163688A1 (enrdf_load_stackoverflow) * 1971-12-15 1973-07-27 Rolls Royce
US3814324A (en) * 1972-06-19 1974-06-04 Gen Electric Propulsion nozzle and actuator system employed therein
US5615834A (en) * 1995-01-31 1997-04-01 Osman; Medhat A. Ultra thrust reverser system
US20040231317A1 (en) * 2001-09-27 2004-11-25 Dehu Michel Philippe Locking system on a grid thrust reverser
US7007454B2 (en) * 2001-09-27 2006-03-07 Hurel Hispano Locking system on a cascade thrust reverser
US20090107108A1 (en) * 2006-05-10 2009-04-30 Guy Bernard Vauchel Nacell for bypass engine with high bypass ratio
US8720182B2 (en) * 2006-10-12 2014-05-13 United Technologies Corporation Integrated variable area nozzle and thrust reversing mechanism
US20100269485A1 (en) * 2006-10-12 2010-10-28 Jain Ashok K Integrated variable area nozzle and thrust reversing mechanism
RU2499904C2 (ru) * 2008-04-14 2013-11-27 Эрсель Гондола двухконтурного турбореактивного двигателя
FR2939477A1 (fr) * 2008-12-10 2010-06-11 Aircelle Sa Nacelle de turboreacteur a section de tuyere variable
WO2010066957A1 (fr) * 2008-12-10 2010-06-17 Aircelle Nacelle de turboreacteur a section de tuyere variable
EP2243945A3 (en) * 2009-04-24 2014-03-26 United Technologies Corporation Thrust reverser assembly with shaped drag links
RU2538348C2 (ru) * 2009-11-05 2015-01-10 Эрсель Устройство реверса тяги
US20150107224A1 (en) * 2013-10-17 2015-04-23 Rohr, Inc. Core cowl thrust reverser system and apparatus
US9650992B2 (en) * 2013-10-17 2017-05-16 Rohr, Inc. Core cowl thrust reverser system and apparatus
US20170198659A1 (en) * 2016-01-13 2017-07-13 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10533519B2 (en) * 2016-01-13 2020-01-14 Rohr, Inc. Translating cascade hidden blocker door thrust reverser

Also Published As

Publication number Publication date
GB1147351A (en) 1969-04-02
CH446078A (de) 1967-10-31
BE682005A (enrdf_load_stackoverflow) 1966-11-14
NL6607772A (enrdf_load_stackoverflow) 1966-12-08
DE1287444B (de) 1969-01-16

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